Abstract
A large-eddy simulation (LES) of a gaseous hydrogen/liquid oxygen (GH2/LOX) single-injector rocket combustor is performed in this study. The Redlich–Kwong–Peng–Robinson (RK–PR) equation of state is used to simulate the real-gas effect under high-pressure conditions, and the steady laminar flamelet model (SLFM) is implemented to simulate fast chemistry, such as a H2/O2 reaction. From the numerical simulation, the characteristics of time-averaged flow and flame fields are obtained, and their relationship with the real-gas effect is investigated. It is possible to investigate unsteady flame features and the mixing mechanism of propellants in detail by examining multiple snapshots of the field contour. Another purpose of the study is to investigate the differences in flow and flame structures according to the variation in the turbulent Schmidt number. By comparing the simulation result with the natural OH* emission image and temperature profiles from experimental data, the appropriate range of the turbulent Schmidt number for the simulation is obtained. Furthermore, this paper suggests the usefulness and validity of the current research by quantitatively comparing (i.e., temperature profiles) numerical results with those of existing literature.
Highlights
The conventional approach to increasing the propulsion performance of a liquid rocket engine for a launch vehicle is to increase combustion pressure
Based on on the the results, results, the the time-averaged time-averaged flow flow and and flame flame structures structures are are first first investigated investigated by by examining the contour fields obtained from the simulation
The average flow and flame structures of the combustor can be investigated by temporal-averaging the obtained flow field data, and the dynamics of the flow and flame can be investigated by analyzing the unsteady flow field data
Summary
The conventional approach to increasing the propulsion performance of a liquid rocket engine for a launch vehicle is to increase combustion pressure. Many experiments have been conducted to visualize the behavior of real-gas fluid and the combustion process and to quantify various parameters in these high-pressure conditions When fuel such as hydrogen is used as a propellant, quantifying the parameters is challenging due to the high combustion temperature (e.g., the insertion type sensor is susceptible to high temperatures), and the visualization technique becomes limited (e.g., shadowgraph, radical emission image). In this case, a numerical simulation can be an alternative and efficient analysis tool. Juniper et al [1] measured the natural OH* emission using the laser-induced fluorescence (LIF) technique for the A60 and C60
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
